CN113623022A - Turbine outer ring with easily-abraded coating - Google Patents
Turbine outer ring with easily-abraded coating Download PDFInfo
- Publication number
- CN113623022A CN113623022A CN202110870084.4A CN202110870084A CN113623022A CN 113623022 A CN113623022 A CN 113623022A CN 202110870084 A CN202110870084 A CN 202110870084A CN 113623022 A CN113623022 A CN 113623022A
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- China
- Prior art keywords
- turbine
- coating
- outer ring
- abradable coating
- blade
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Coating By Spraying Or Casting (AREA)
Abstract
The application belongs to the field of aeroengine turbine outer rings, and particularly relates to a turbine outer ring with an easily-abraded coating. The turbine outer ring is provided with an annular profile opposite to the turbine rotor blades, the annular profile is coated with an easily-worn coating with a preset thickness in a low-pressure plasma spraying mode, and the thickness of the easily-worn coating satisfies the following requirements: h is not less than D-D and H is more than 0; h is the thickness of the easily-abraded coating, D is the maximum value of rotor clearance change in the working process of the engine, and D is the cold-state clearance of the rotor and the stator of the turbine blade tip. The material selection of the easily-abraded coating meets the following requirements: the hardness of the material of the easily-abraded coating is lower than that of the blade tip of the turbine rotor blade; the material of the easy-wear coating has abradability; and the material of the easily-abraded coating and the base material of the outer ring of the turbine have certain combination characteristics. This application can alleviate the vibration excitation when changeing, stator radially bump the mill, can reduce turbine blade apex wearing and tearing simultaneously, keeps turbine performance and blade working capacity, promotes blade life.
Description
Technical Field
The application belongs to the field of aeroengine turbine outer rings, and particularly relates to a turbine outer ring with an easily-abraded coating.
Background
The turbine blade tip clearance has very important influence on the efficiency and the performance of related mechanical systems, the control of the blade tip clearance has great significance for improving the system efficiency, and the turbine blade tip clearance also has very deep influence on the exhaust temperature, the service life of parts, the working reliability and the like of mechanical systems such as aircraft engines, gas turbines and the like. The clearance is too small, so that the rotor and the stator are easy to rub, part abrasion and system performance attenuation are caused, and the rotor can vibrate even seriously break down in serious conditions, so that the use safety of the product is threatened. Because the turbine blade tip clearance is influenced by multiple factors such as rotor and stator concentricity, high-temperature deformation of parts, rotor and stator thermal deformation rate difference and the like, the difficulty in stably controlling the blade tip clearance is very high, and how to control the rotor and stator clearance of the turbine part is also an important subject in the industry.
In the prior art, a coated turbine outer ring is not available, so that the abrasion of the blade tip caused by the collision with the blade tip can be inevitably caused in use, the abrasion of the blade tip is caused, the crack of the blade tip is easily induced, the service life of the blade is adversely affected, and the problem of rotor vibration is easily induced by violent collision and abrasion; and simultaneously, the blade tip clearance is increased due to the abrasion of the blade tip.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a turbine outer ring with an abradable coating to address at least one of the problems with the prior art.
The technical scheme of the application is as follows:
a turbine outer ring having an abradable coating, comprising:
the turbine outer ring is provided with an annular profile opposite to the turbine rotor blades, the annular profile is coated with an easily-worn coating with a preset thickness by means of low-pressure plasma spraying, and the thickness of the easily-worn coating satisfies the following requirements:
h is not less than D-D and H is more than 0;
h is the thickness of the easily-abraded coating, D is the maximum value of rotor clearance change in the working process of the engine, and D is the cold-state clearance of the rotor and the stator of the turbine blade tip.
In at least one embodiment of the present application, the material of the abradable coating has abradable properties.
In at least one embodiment of the present application, the hardness of the abradable coating and the hardness of the turbine rotor blade tip are such that, at any time during the entire operation of the engine: a < B, wherein A is the hardness of the abradable coating, and B is the hardness of the tip of the turbine rotor blade.
In at least one embodiment of the present application, the material of the abradable coating has a bond characteristic with the turbine outer ring substrate material, and the bond strength is greater than 35 Mpa.
In at least one embodiment of the present application, the abradable coating is a CoNiCrAlY powder.
In at least one embodiment of the present application, the abradable coating is disposed in a full ring along the annular profile of the turbine outer ring.
In at least one embodiment of the present application, the abradable coating is spaced on the annular profile of the turbine outer ring.
The invention has at least the following beneficial technical effects:
the utility model provides a turbine outer loop with easy wearing coating, through the easy wearing coating of applying predetermined thickness on the annular profile of turbine outer loop, can alleviate the vibration excitation when changeing, stator radially bump the mill, can reduce turbine blade apex wearing and tearing simultaneously, keep turbine performance and blade working capacity, promote blade life.
Drawings
FIG. 1 is an assembly view of a turbine outer ring having an abradable coating in accordance with an embodiment of the present application;
FIG. 2 is a schematic view of an outer ring of a turbine having an abradable coating in accordance with an embodiment of the present application.
Wherein:
1-a turbine outer ring; 2-an easily abradable coating; 3-turbine rotor blades.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The present application is described in further detail below with reference to fig. 1-2.
The present application provides a turbine outer ring with an abradable coating, comprising: an outer turbine ring 1 coated with an abradable coating 2.
Specifically, as shown in fig. 1, the turbine outer ring 1 has an annular profile opposite to the turbine rotor blades 3, and the annular profile of the turbine outer ring 1 is coated with an easily-abradable coating 2 with a predetermined thickness by means of low-pressure plasma spraying, and the thickness of the easily-abradable coating 2 satisfies:
h is not less than D-D and H is more than 0;
h is the thickness of the easily-abraded coating, D is the maximum value of rotor clearance change in the working process of the engine, and D is the cold-state clearance of the rotor and the stator of the turbine blade tip.
The turbine outer ring with the easily-abraded coating prevents the abrasion of the blade tip by coating the easily-abraded coating 2 on the annular profile of the turbine outer ring 1 corresponding to the turbine rotor blade 3. In a preferred embodiment of the present application, the material of the abradable coating 2 is selected to meet the following requirements: the material of the abradable coating 2 has abradable properties. The abradable property of the abradable coating 2 is embodied in that the hardness of the abradable coating 2 and the hardness of the tip of the turbine rotor blade 3 are satisfied at any time during the entire operation of the engine: a < B, wherein A is the hardness of the wear-resistant coating, B is the hardness of the blade tip of the turbine rotor blade, and A, B is changed according to different working conditions of the engine. Moreover, in the present embodiment, the material of the easy-to-wear coating 2 and the base material of the turbine outer ring 1 have certain bonding characteristics, and the bonding characteristics of the easy-to-wear coating 2 and the base material of the turbine outer ring 1 are represented by that after the easy-to-wear coating 2 is sprayed on the base material of the turbine outer ring 1, the easy-to-wear coating 2 has a uniform structure, small pores, and good bonding with the base interface, and the bonding strength should be greater than 35 Mpa.
In the preferred embodiment of the application, the abradable coating 2 is a CoNiCrAlY powder, which is applied to the base material of the turbine outer ring 1 to a certain thickness by means of low-pressure plasma spraying. When a mechanical system is subjected to radial collision and abrasion of a rotor and a stator due to factors such as thermal deformation incompatibility, the characteristic that the easily-abraded coating 2 on the turbine outer ring 1 can be abraded is utilized, the situation that the turbine outer ring 1 and the blade tips of the turbine rotor blades 3 are hard to collide is relieved, vibration caused by collision and abrasion is weakened, and meanwhile the effect of reducing abrasion of the blade tips of the turbine blades can be achieved.
In a preferred embodiment of the present application, the abradable coating 2 may be arranged in a full ring along the annular profile of the turbine outer ring 1, as shown in fig. 2. In another embodiment of the present application, the abradable coating 2 is spaced apart on the annular profile of the turbine outer ring 1. In other embodiments of the present application, it is also possible to obtain the region where the turbine rotor blade 3 is rubbed heavily according to the real turbine rotor blade, and the abradable coating 2 is disposed on the region where the turbine outer ring 1 is rubbed heavily by the annular profile, so as to achieve the effect of alleviating the rotor stator rub-in.
The utility model provides a turbine outer loop with easy wearing coating, through the easy wearing coating of applying predetermined thickness on the annular profile of turbine outer loop, can alleviate and change, the stator radially bumps the excitation of grinding to the vibration, can reduce turbine blade apex wearing and tearing simultaneously, keeps turbine performance and blade working capacity, promotes blade life, reduces the adverse effect of factors such as concentricity change, spare part deformation to apex clearance.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A turbine outer ring having an abradable coating, comprising:
the turbine outer ring (1) is provided with an annular profile opposite to a turbine rotor blade (3), the annular profile is coated with an easily-worn coating (2) with a preset thickness by means of low-pressure plasma spraying, and the thickness of the easily-worn coating (2) satisfies the following conditions:
h is not less than D-D and H is more than 0;
h is the thickness of the easily-abraded coating, D is the maximum value of rotor clearance change in the working process of the engine, and D is the cold-state clearance of the rotor and the stator of the turbine blade tip.
2. The outer ring of a turbine having an abradable coating according to claim 1, characterized in that the material of the abradable coating (2) has abradable properties.
3. The outer ring of a turbine having an abradable coating according to claim 2, characterized in that the hardness of the abradable coating (2) and the hardness of the tip of the turbine rotor blade (3) are such that, at any time during the entire operation of the engine: a < B, wherein A is the hardness of the abradable coating, and B is the hardness of the tip of the turbine rotor blade.
4. The outer turbine ring with an abradable coating according to claim 3, characterized in that the material of the abradable coating (2) has a bonding property with the base material of the outer turbine ring (1) and a bonding strength greater than 35 Mpa.
5. The outer ring of a turbine having an abradable coating according to claim 4, characterized in that the abradable coating (2) is a CoNiCrAlY powder.
6. The turbine outer ring with an abradable coating according to claim 1, characterized in that the abradable coating (2) is arranged in a full ring along the annular profile of the turbine outer ring (1).
7. The turbine outer ring with an abradable coating according to claim 1, characterized in that the abradable coating (2) is spaced apart on the annular profile of the turbine outer ring (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110870084.4A CN113623022A (en) | 2021-07-30 | 2021-07-30 | Turbine outer ring with easily-abraded coating |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110870084.4A CN113623022A (en) | 2021-07-30 | 2021-07-30 | Turbine outer ring with easily-abraded coating |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113623022A true CN113623022A (en) | 2021-11-09 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110870084.4A Pending CN113623022A (en) | 2021-07-30 | 2021-07-30 | Turbine outer ring with easily-abraded coating |
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| CN (1) | CN113623022A (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013026870A1 (en) * | 2011-08-22 | 2013-02-28 | Siemens Aktiengesellschaft | Turbomachine comprising a coated rotor blade tip and a coated inner housing |
| CN104718349A (en) * | 2012-10-11 | 2015-06-17 | 涡轮梅坎公司 | Rotor-stator assembly for a gas-turbine engine |
| CN108486567A (en) * | 2018-04-03 | 2018-09-04 | 江西省科学院应用物理研究所 | A kind of preparation method of single crystal turbine blade blade tip nano-particle reinforcement wear-resistant coating |
| US20190242261A1 (en) * | 2018-02-02 | 2019-08-08 | United Technologies Corporation | Wear resistant turbine blade tip |
| CN112343855A (en) * | 2021-01-08 | 2021-02-09 | 中国航发上海商用航空发动机制造有限责任公司 | Aeroengine and method for evaluating blade tip clearance of aeroengine on wing |
| CN112601841A (en) * | 2018-08-22 | 2021-04-02 | 赛峰飞机发动机公司 | Abradable coating for rotating blades of a turbomachine |
-
2021
- 2021-07-30 CN CN202110870084.4A patent/CN113623022A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2013026870A1 (en) * | 2011-08-22 | 2013-02-28 | Siemens Aktiengesellschaft | Turbomachine comprising a coated rotor blade tip and a coated inner housing |
| CN104718349A (en) * | 2012-10-11 | 2015-06-17 | 涡轮梅坎公司 | Rotor-stator assembly for a gas-turbine engine |
| US20190242261A1 (en) * | 2018-02-02 | 2019-08-08 | United Technologies Corporation | Wear resistant turbine blade tip |
| CN108486567A (en) * | 2018-04-03 | 2018-09-04 | 江西省科学院应用物理研究所 | A kind of preparation method of single crystal turbine blade blade tip nano-particle reinforcement wear-resistant coating |
| CN112601841A (en) * | 2018-08-22 | 2021-04-02 | 赛峰飞机发动机公司 | Abradable coating for rotating blades of a turbomachine |
| CN112343855A (en) * | 2021-01-08 | 2021-02-09 | 中国航发上海商用航空发动机制造有限责任公司 | Aeroengine and method for evaluating blade tip clearance of aeroengine on wing |
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Application publication date: 20211109 |